U.S. patent number 10,161,255 [Application Number 15/019,442] was granted by the patent office on 2018-12-25 for turbine nozzle having non-axisymmetric endwall contour (ewc).
This patent grant is currently assigned to General Electric Company. The grantee listed for this patent is General Electric Company. Invention is credited to Lee Larned Brozyna, Christopher Lee Golden, Christopher Donald Porter.
United States Patent |
10,161,255 |
Brozyna , et al. |
December 25, 2018 |
Turbine nozzle having non-axisymmetric endwall contour (EWC)
Abstract
Various embodiments of the invention include turbine nozzles and
systems employing such nozzles. Various particular embodiments
include a turbine nozzle having: an airfoil having: a suction side;
a pressure side opposing the suction side; a leading edge spanning
between the pressure side and the suction side; and a trailing edge
opposing the leading edge and spanning between the pressure side
and the suction side; and at least one endwall connected with the
airfoil along the suction side, pressure side, trailing edge and
the leading edge, the at least one endwall including a
non-axisymmetric contour proximate a junction between the endwall
and the leading edge of the airfoil.
Inventors: |
Brozyna; Lee Larned (Mauldin,
SC), Golden; Christopher Lee (Greer, SC), Porter;
Christopher Donald (Greenville, SC) |
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
59497458 |
Appl.
No.: |
15/019,442 |
Filed: |
February 9, 2016 |
Prior Publication Data
|
|
|
|
Document
Identifier |
Publication Date |
|
US 20170226878 A1 |
Aug 10, 2017 |
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F01D
5/145 (20130101); F01D 9/041 (20130101); F01D
5/143 (20130101); F05D 2220/31 (20130101); F05D
2220/32 (20130101); Y02T 50/673 (20130101); F05D
2250/74 (20130101); F05D 2240/121 (20130101); F05D
2240/128 (20130101); F05D 2250/73 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
F01D
9/04 (20060101); F01D 5/14 (20060101) |
References Cited
[Referenced By]
U.S. Patent Documents
Other References
US. Appl. No. 15/019,516, Office Action 1 dated Nov. 21, 2017, 15
pages. cited by applicant .
U.S. Appl. No. 15/019,426, Office Action 1 dated Dec. 29, 2017, 11
pages. cited by applicant .
U.S. Appl. No. 15/019,461, Office Action 1 dated Jan. 5, 2018, 14
pages. cited by applicant .
U.S. Appl. No. 15/019,476, Office Action 1 dated Jan. 5, 2018, 14
pages. cited by applicant .
U.S. Appl. No. 15/019,487, Office Action 1 dated Jan. 5, 2018, 13
pages. cited by applicant .
U.S. Appl. No. 15/019,502, Office Action 1 dated Jan. 5, 2018, 13
pages. cited by applicant .
U.S. Appl. No. 15/019,379 Office Action dated Mar. 19, 2018, 21
pages. cited by applicant .
U.S. Appl. No. 15/019,516, Notice of Allowance dated Apr. 6, 2018,
14 pages. cited by applicant .
U.S. Appl. No. 15/019,426, Office Action dated Jun. 12, 2018, 19
pages. cited by applicant .
U.S. Appl. No. 15/019,487, Final Office Action dated Jun. 14, 2018,
17 pages. cited by applicant .
U.S. Appl. No. 15/019,461, Final Office Action dated Jun. 29, 2018,
16 pages. cited by applicant .
U.S. Appl. No. 15/019,476, Final Office Action dated Jun. 29, 2018,
17 pages. cited by applicant .
U.S. Appl. No. 15/019,502, Final Office Action dated Jun. 29, 2018,
16 pages. cited by applicant .
U.S. Appl. No. 15/019,426, Notice of Allowance dated Sep. 12, 2018,
11 pages. cited by applicant .
U.S. Appl. No. 15/019,461, Notice of Allowance dated Sep. 17, 2018,
11 pages. cited by applicant .
U.S. Appl. No. 15/019,487, Notice of Allowance dated Sep. 18, 2018,
13 pages. cited by applicant .
U.S. Appl. No. 15/019,379, Notice of Allowance dated Sep. 25, 2018,
9 pages. cited by applicant .
U.S. Appl. No. 15/019,502, Notice of Allowance dated Oct. 24, 2018,
11 pages. cited by applicant.
|
Primary Examiner: Brockman; Eldon T
Attorney, Agent or Firm: Cusick; Ernest G. Hoffman Warnick
LLC
Claims
We claim:
1. A turbine nozzle comprising: an airfoil having: a suction side;
a pressure side opposing the suction side; a leading edge spanning
between the pressure side and the suction side; and a trailing edge
opposing the leading edge and spanning between the pressure side
and the suction side; and at least one endwall connected with the
airfoil along the suction side, pressure side, trailing edge and
the leading edge, the at least one endwall including a
non-axisymmetric contour proximate a junction between the endwall
and the leading edge of the airfoil, wherein the non-axisymmetric
contour includes three distinct leading edge features, the three
distinct leading edge features including a leading edge pressure
side feature, a leading edge suction side feature and a mid-passage
feature, wherein the leading edge pressure side feature of the
non-axisymmetric contour includes a thickened area having an apex
at approximately 5% axial chord upstream of the leading edge, and
wherein the non-axisymmetric contour further includes a passage
trough on the pressure side of the airfoil, wherein the passage
trough includes a depression having an apex at approximately 60% of
a chord length of the pressure side of the airfoil, wherein the
depression spans approximately 40% to 60% pitch as measured from
the pressure side of the airfoil, wherein the at least one endwall
directs flow of a working fluid through the passage trough.
2. The turbine nozzle of claim 1, further comprising a fillet
connecting a surface of the endwall to a surface of the
airfoil.
3. The turbine nozzle of claim 1, wherein the turbine nozzle
includes a second stage nozzle.
4. The turbine nozzle of claim 1, wherein the at least one endwall
includes an inner endwall or an outer endwall.
5. The turbine nozzle of claim 1, wherein the thickened area
extends across at least approximately 10 percent of an axial length
of the endwall, and has a pitch of approximately zero percent to
approximately 10 percent from the suction side.
6. The turbine nozzle of claim 1, wherein the thickened area
extends across approximately 20 percent to approximately 30 percent
of an axial length of the endwall.
7. The turbine nozzle of claim 1, wherein at least one of the
suction side or the pressure side of the airfoil includes a nominal
profile substantially in accordance with Cartesian coordinate
values of X, Y and Z set forth in TABLE I, wherein the coordinate
values are non-dimensional values of from 0 to 1 convertible to
distances by multiplying the values by a trailing edge height
expressed in units of distance, and wherein X and Y values
connected by smooth continuing arcs define airfoil profile sections
at each distance Z along the airfoil, the profile sections at the Z
distances being joined smoothly with one another to form the
airfoil profile, wherein the Cartesian coordinate values have an
origin at a root of the leading edge of the airfoil.
8. A static nozzle section comprising: a set of static nozzles, the
set of static nozzles including at least one nozzle having: an
airfoil having: a suction side; a pressure side opposing the
suction side; a leading edge spanning between the pressure side and
the suction side; and a trailing edge opposing the leading edge and
spanning between the pressure side and the suction side; and at
least one endwall connected with the airfoil along the suction
side, pressure side, trailing edge and the leading edge, the at
least one endwall including a non-axisymmetric contour proximate a
junction between the endwall and the leading edge of the airfoil,
wherein at least one of the suction side or the pressure side of
the airfoil includes a nominal profile substantially in accordance
with Cartesian coordinate values of X, Y and Z set forth in TABLE
I, wherein the coordinate values are non-dimensional values of from
0 to 1 convertible to distances by multiplying the values by a
trailing edge height expressed in units of distance, and wherein X
and Y values connected by smooth continuing arcs define airfoil
profile sections at each distance Z along the airfoil, the profile
sections at the Z distances being joined smoothly with one another
to form the airfoil profile, wherein the Cartesian coordinate
values have an origin at a root of the leading edge of the
airfoil.
9. The static nozzle section of claim 8, further comprising a
fillet connecting a surface of the endwall to a surface of the
airfoil.
10. The static nozzle section of claim 8, wherein the turbine
nozzle includes a second stage nozzle.
11. The static nozzle section of claim 8, wherein the
non-axisymmetric contour includes a thickened area having an apex
at approximately 5% axial chord upstream of the leading edge.
12. The static nozzle section of claim 11, wherein the thickened
area extends across at least approximately 10 percent of an axial
length of the endwall, and has a pitch of approximately zero
percent to approximately 10 percent from the suction side.
13. The static nozzle section of claim 11, wherein the thickened
area extends across approximately 20 percent to approximately 30
percent of an axial length of the endwall.
14. The static nozzle section of claim 8, wherein the at least one
endwall directs flow of a working fluid through a passage trough
proximate the pressure side of the airfoil.
15. A turbine nozzle comprising: an airfoil having: a suction side;
a pressure side opposing the suction side; a leading edge spanning
between the pressure side and the suction side; and a trailing edge
opposing the leading edge and spanning between the pressure side
and the suction side; and at least one endwall connected with the
airfoil along the suction side, pressure side, trailing edge and
the leading edge, wherein at least one of the pressure side or the
suction side of the airfoil includes a nominal profile
substantially in accordance with Cartesian coordinate values of X,
Y and Z set forth in TABLE I, wherein the coordinate values are
non-dimensional values of from 0 to 1 convertible to distances by
multiplying the values by a trailing edge height expressed in units
of distance, and wherein X and Y values connected by smooth
continuing arcs define airfoil profile sections at each distance Z
along the airfoil, the profile sections at the Z distances being
joined smoothly with one another to form the airfoil profile,
wherein the Cartesian coordinate values have an origin at a root of
the leading edge of the airfoil.
16. The turbine nozzle of claim 15, wherein the at least one
endwall includes a non-axisymmetric contour proximate a junction
between the endwall and the leading edge of the airfoil.
17. The turbine nozzle of claim 16, wherein the non-axisymmetric
contour includes a thickened area having an apex at approximately
5% axial chord upstream of the leading edge.
18. The turbine nozzle of claim 16, wherein the thickened area
extends across at least approximately 10 percent of an axial length
of the endwall, and has a pitch of approximately zero percent to
approximately 10 percent from the suction side.
Description
FIELD OF THE INVENTION
The subject matter disclosed herein relates to turbomachines. More
particularly, the subject matter disclosed herein relates to
components within turbomachines such as gas and/or steam
turbines.
BACKGROUND OF THE INVENTION
Some aircraft and/or power plant systems, for example certain jet
aircraft, nuclear, simple cycle and combined cycle power plant
systems, employ turbines (also referred to as turbomachines) in
their design and operation. Some of these turbines employ airfoils
(e.g., turbine blades, blades, airfoils, etc.) which during
operation are exposed to fluid flows. These airfoils are configured
to aerodynamically interact with the fluid flows and generate
energy (e.g., creating thrust, turning kinetic energy to mechanical
energy, thermal energy to mechanical energy, etc.) from these fluid
flows as part of power generation. As a result of this interaction
and conversion, the aerodynamic characteristics and losses of these
airfoils have an impact on system and turbine operation,
performance, thrust, efficiency, and power.
BRIEF DESCRIPTION OF THE INVENTION
Various embodiments of the invention include turbine nozzles and
systems employing such nozzles. Various particular embodiments
include a turbine nozzle having: an airfoil having: a suction side;
a pressure side opposing the suction side; a leading edge spanning
between the pressure side and the suction side; and a trailing edge
opposing the leading edge and spanning between the pressure side
and the suction side; and at least one endwall connected with the
airfoil along the suction side, pressure side, trailing edge and
the leading edge, the at least one endwall including a
non-axisymmetric contour proximate a junction between the endwall
and the leading edge of the airfoil.
A first aspect of the invention includes a turbine nozzle having:
an airfoil having: a suction side; a pressure side opposing the
suction side; a leading edge spanning between the pressure side and
the suction side; and a trailing edge opposing the leading edge and
spanning between the pressure side and the suction side; and at
least one endwall connected with the airfoil along the suction
side, pressure side, trailing edge and the leading edge, the at
least one endwall including a non-axisymmetric contour proximate a
junction between the endwall and the leading edge of the
airfoil.
A second aspect of the invention includes a static nozzle section
having: a set of static nozzles, the set of static nozzles
including at least one nozzle having: an airfoil having: a suction
side; a pressure side opposing the suction side; a leading edge
spanning between the pressure side and the suction side; and a
trailing edge opposing the leading edge and spanning between the
pressure side and the suction side; and at least one endwall
connected with the airfoil along the suction side, pressure side,
trailing edge and the leading edge, the at least one endwall
including a non-axisymmetric contour proximate a junction between
the endwall and the leading edge of the airfoil, wherein at least
one of the suction side or the pressure side of the airfoil
includes a nominal profile substantially in accordance with
Cartesian coordinate values of X, Y and Z set forth in TABLE I,
wherein the coordinate values are non-dimensional values of from 0
to 1 convertible to distances by multiplying the values by a
trailing edge height expressed in units of distance, and wherein X
and Y values connected by smooth continuing arcs define airfoil
profile sections at each distance Z along the airfoil, the profile
sections at the Z distances being joined smoothly with one another
to form the airfoil profile, wherein the Cartesian coordinate
values have an origin at a root of the leading edge of the
airfoil.
A third aspect of the invention includes a turbine nozzle
comprising: an airfoil having: a suction side; a pressure side
opposing the suction side; a leading edge spanning between the
pressure side and the suction side; and a trailing edge opposing
the leading edge and spanning between the pressure side and the
suction side; and at least one endwall connected with the airfoil
along the suction side, pressure side, trailing edge and the
leading edge, wherein at least one of the pressure side or the
suction side of the airfoil includes a nominal profile
substantially in accordance with Cartesian coordinate values of X,
Y and Z set forth in TABLE I, wherein the coordinate values are
non-dimensional values of from 0 to 1 convertible to distances by
multiplying the values by a trailing edge height expressed in units
of distance, and wherein X and Y values connected by smooth
continuing arcs define airfoil profile sections at each distance Z
along the airfoil, the profile sections at the Z distances being
joined smoothly with one another to form the airfoil profile,
wherein the Cartesian coordinate values have an origin at a root of
the leading edge of the airfoil.
BRIEF DESCRIPTION OF THE DRAWINGS
These and other features of this invention will be more readily
understood from the following detailed description of the various
aspects of the invention taken in conjunction with the accompanying
drawings that depict various embodiments of the invention, in
which:
FIG. 1 shows a three-dimensional partial cut-away perspective view
of a portion of a turbine according to an embodiment of the
invention.
FIG. 2 shows a schematic three-dimensional depiction of a turbine
nozzle including an airfoil and endwalls according to various
embodiments of the invention.
FIG. 3 shows an example contour plot of an area along the endwall
surrounding the airfoil of FIG. 2 according to various embodiments
of the invention.
FIG. 4 shows a schematic three-dimensional depiction of a plurality
of turbine nozzles according to various embodiments of the
invention.
FIG. 5 shows a schematic block diagram illustrating portions of a
multi-shaft combined cycle power plant system according to
embodiments of the invention; and
FIG. 6 shows a schematic block diagram illustrating portions of a
single-shaft combined cycle power plant system according to
embodiments of the invention.
It is noted that the drawings of the invention are not necessarily
to scale. The drawings are intended to depict only typical aspects
of the invention, and therefore should not be considered as
limiting the scope of the invention. It is understood that elements
similarly numbered between the FIGURES may be substantially similar
as described with reference to one another. Further, in embodiments
shown and described with reference to FIGS. 1-6, like numbering may
represent like elements. Redundant explanation of these elements
has been omitted for clarity. Finally, it is understood that the
components of FIGS. 1-6 and their accompanying descriptions may be
applied to any embodiment described herein.
DETAILED DESCRIPTION OF THE INVENTION
As noted herein, various aspects of the invention are directed
toward turbine nozzles. Particular aspects of the invention include
turbine nozzles having at least one endwall with a non-axisymmetric
contour.
In contrast to conventional turbine nozzles, aspects of the
invention include a turbine nozzle (e.g., a static nozzle for
directing a working fluid such as gas or steam) having a
non-axisymmetric contour at the leading edge of its endwall. This
non-axisymmetric contour can provide for enhanced performance,
efficiency and/or durability of the nozzle (and associated turbine
stages and turbine machines) when compared with conventional
nozzles.
As used herein, the terms "axial" and/or "axially" refer to the
relative position/direction of objects along axis A, which is
substantially parallel to the axis of rotation of the turbomachine
(in particular, the rotor section). As further used herein, the
terms "radial" and/or "radially" refer to the relative
position/direction of objects along axis (r), which is
substantially perpendicular with axis A and intersects axis A at
only one location. Additionally, the terms "circumferential" and/or
"circumferentially" refer to the relative position/direction of
objects along a circumference which surrounds axis A but does not
intersect the axis A at any location. Further, the terms leading
edge/pressure side refer to components and/or surfaces which are
oriented predominately upstream relative to the fluid flow of the
system, and the terms trailing edge/suction side refer to
components and/or surfaces which are oriented predominately
downstream relative to the fluid flow of the system.
In the following description, reference is made to the accompanying
drawings that form a part thereof, and in which is shown by way of
illustration specific embodiments in which the present teachings
may be practiced. These embodiments are described in sufficient
detail to enable those skilled in the art to practice the present
teachings and it is to be understood that other embodiments may be
utilized and that changes may be made without departing from the
scope of the present teachings. The following description is,
therefore, merely exemplary.
Referring to the drawings, FIG. 1 shows a perspective partial
cut-away illustration of a turbine 10 (e.g., a gas or steam turbine
and/or an aviation jet engine) according to various embodiments of
the invention. Turbine 10 includes a rotor 12 that includes a
rotating shaft 14 and a plurality of axially spaced rotor wheels
18. A plurality of rotating buckets 20 are mechanically coupled to
each rotor wheel 18. More specifically, buckets 20 are arranged in
rows that extend circumferentially around each rotor wheel 18. A
static nozzle section 21 is shown including a plurality of
stationary nozzles 22 that circumferentially around shaft 14, and
the nozzles 22 are axially positioned between adjacent rows of
buckets 20. Stationary nozzles 22 cooperate with buckets 20 to form
a stage of the turbine 10, and to define a portion of a flow path
through turbine 10. As shown, the static nozzle section 21 at least
partially surrounds the rotor 12 (shown in this cut-away view). It
is understood that the turbine 10 shown is a dual-flow turbine 10
that includes an axially centered inlet mouth which feeds two sets
of turbine stages. It is understood that various teachings can be
applied to axial turbines, e.g., axial inlet gas turbines that
inlet a combustion gas from a first axial end and outlet that
combustion gas to a second axial end after the gas has performed
mechanical work on the turbine.
Returning to FIG. 1, in operation, gas 24 enters an inlet 26 of
turbine 10 and is channeled through stationary nozzles 22. Nozzles
22 direct gas 24 against blades 20. Gas 24 passes through the
remaining stages imparting a force on buckets 20 causing shaft 14
to rotate. At least one end of turbine 10 may extend axially away
from rotating shaft 12 and may be attached to a load or machinery
(not shown) such as, but not limited to, a generator, and/or
another turbine.
In one embodiment, turbine 10 may include five stages. The five
stages are referred to as L0, L1, L2, L3 and L4. Stage L4 is the
first stage and is the smallest (in a radial direction) of the five
stages. Stage L3 is the second stage and is the next stage in an
axial direction. Stage L2 is the third stage and is shown in the
middle of the five stages. Stage L1 is the fourth and next-to-last
stage. Stage L0 is the last stage and is the largest (in a radial
direction). It is to be understood that five stages are shown as
one example only, and each turbine may have more or less than five
stages. Also, as will be described herein, the teachings of the
invention do not require a multiple stage turbine. In another
embodiment, turbine 10 may comprise an aircraft engine used to
produce thrust.
Turning to FIG. 2, a schematic three-dimensional depiction of a
turbine nozzle (or simply, nozzle) 200 is shown according to
various embodiments. The nozzle 200 is a stationary nozzle which
forms an annulus of stationary nozzles in a stage of a turbine
(e.g., turbine 10). That is, during operation of a turbine (e.g.,
turbine 10), the nozzle 200 will remain stationary in order to
direct the flow of working fluid (e.g., gas or steam) to one or
more movable buckets (e.g., buckets 20), causing those movable
buckets to initiate rotation of a rotor shaft (e.g., shaft 14). It
is understood that nozzle 200 is configured to couple (mechanically
couple via fasteners, welds, slot/grooves, etc.) with a plurality
of similar or distinct nozzles (e.g., nozzles 200 or other nozzles)
to form an annulus of nozzles in a stage of the turbine.
Returning to FIG. 2, the turbine nozzle 200 can include an airfoil
202 having a suction side 204, and a pressure side 206 (obstructed
in this view) opposing the suction side 204. The nozzle 200 can
also include a leading edge 208 spanning between the pressure side
206 and the suction side 204, and a trailing edge 210 opposing the
leading edge 208 and spanning between the pressure side 206 and the
suction side 204.
As shown, the nozzle 200 can also include at least one endwall 212
(two shown) connected with the airfoil 202. The nozzle 200 can be
connected with the airfoil 202 along the suction side 204, pressure
side 206, trailing edge 210 and the leading edge 208. In various
embodiments, the nozzle includes a fillet 214 connecting the nozzle
210 and each endwall 212. The fillet 214 can include a weld or
braze fillet, which may be formed via conventional MIG welding, TIG
welding, brazing, etc.
As described herein, and in contrast to conventional turbine
nozzles, the turbine nozzle 200 can include at least one endwall
212 with a non-axisymmetric contour 218 proximate a junction 220
between the endwall 212 and the leading edge 208 of the airfoil
202. That is, the nozzle 200 includes an endwall 212 with a contour
218 proximate the junction 220 between the endwall 212 and the
leading edge 208 of the airfoil 202 that improves the flow area
around the airfoil 202 when compared with conventional nozzles.
In various embodiments, the contour 218 allows for more efficient
fluid flow across the airfoil 202 than conventional nozzles 200,
allowing for fewer heat load-related failures, and improving the
efficiency of fluid flow within a turbine utilizing such a nozzle
200.
With reference to FIG. 1, in various embodiments, the nozzle 200
can include a first stage nozzle (L4) or second stage nozzle (L3).
In particular embodiments, the nozzle 200 is a second stage nozzle
(L3), and the improved flow profile across the airfoil 200 and
endwall 212 interface allows that second stage nozzle (L3) to
withstand the high-temperature gas entering the turbine 10 at that
first stage. In various embodiments, the turbine 10 can include a
set of nozzles 200 in only the second stage (L3) of the turbine 10,
or in only the first stage (L4) and the second stage (L3) of the
turbine 10.
In various embodiments, at least one of the endwalls 212 including
the contour 218 can include an inner endwall, e.g., a radially
inner endwall configured to align on the radially inner side of a
the static nozzle section. In other embodiments, at least one of
the endwalls 212 including the contour 218 can include an outer
endwall, e.g., a radially outer endwall configured to align on the
radially outer side of the static nozzle section. In some cases,
both endwalls 212 include the contour 218, and in other cases, only
one of the endwalls 212 includes the contour 218.
According to various embodiments, the non-axisymmetric contour 218
includes a first surface 222 along the endwall 212 on the suction
side 204 of the leading edge 208, and a second surface 224 along
the endwall 212 on the pressure side 206 of the leading edge 208.
The second surface 224 and the first surface 222 can have distinct
slopes, e.g., distinct radial v. circumferential ratios. In various
embodiments, the first surface 222 has a distinct profile from the
second surface 224. In some cases, the distinct profile includes
distinct endwall features (e.g., bump(s), trough(s), etc.) in the
first surface 222 as compared with the second surface 224 (having
its own endwall features (e.g., bump(s), trough(s), etc.). In some
cases, the second surface 224 has a substantially flat, or unsloped
gradient, and the first surface 222 has a gradient distinct from
the gradient of the second surface 224, e.g., a gradient that is
positive or negative, but not equal to zero.
According to various particular embodiments, the first surface 222
has a first length L1 measured from a junction 228 of the suction
side 204 and the leading edge 208 of the airfoil 202 along the
endwall 212 to an outer edge 230 of the endwall 212. In these
embodiments, the second surface 224 has a second length L2 measured
from a junction 232 of the pressure side 206 and the leading edge
208 of the airfoil 202 along the endwall 212 to an inner edge 234
of the endwall 212. In various embodiments, the first length L1 is
distinct from the second length L2, and in particular embodiments,
the second length L2 is greater than the first length L1.
Turning to FIG. 3, a radial contour map of a portion of the endwall
212 (excluding the nozzle 200) is shown according to various
embodiments. As can be seen in this example radial contour map, the
contour 218 (shown in three parts as a leading edge pressure side
feature 218A, a leading edge suction side feature 218B and a
mid-passage feature 218C) can aid in improving aerodynamic
efficiency proximate the leading edge 208 of the nozzle 200. The
radial contour map also shows a passage trough 250 on the pressure
side 206 of the nozzle 200.
With reference to FIG. 2 and FIG. 3, according to various
particular embodiments, the non-axisymmetric contour 218 includes
at least one bump (thickened area) 260 and a passage trough 250 on
the pressure side 206 of the nozzle 200. In particular embodiments,
the leading edge pressure side feature 218A can include at least
one bump (thickened area) 260, and the leading edge suction side
feature 218B and mid passage feature 218C can include at least one
bump (thickened area) 260. It is understood that according to
various embodiments, the bump (thickened area) 260 along the
leading edge pressure side 218A can be thinner than the bump 260
along the leading edge suction side 218B (extending a lesser
distance toward the opposite endwall 212 from the second surface
224 than the bump 260 extends toward the opposite endwall from the
first surface 222).
In various particular embodiments, each bump (thickened area) 260
can extend across approximately at least 10 percent of the axial
length L.sub.A (along axis A) of the endwall 212. In some
particular cases, each thickened area 260 can extend across
approximately 20-30 percent of the axial length L.sub.A of the
endwall 212.
In various particular embodiments, at least one bump 260 (within
218A) can have an apex at approximately 0% axial chord upstream of
the leading edge 208 (+/-5%). In these cases, the bump 260 can span
approximately 10-20% pitch as measured from the pressure side
206.
In other particular embodiments, at least one bump 260 (e.g.,
within 218B) has an apex at approximately 5% of the axial cord
length upstream of the leading edge 208 (+/-5%). In these cases,
the bump 260 can span approximately 0-10% pitch as measured from
the suction side 204.
In another embodiment, at least one bump 260 (within 218C) has an
apex at approximately 40-60% pitch as measured from pressure side
206. This bump 260 may span approximately 10-20% pitch.
In various embodiments, the passage trough 250 includes a
depression having an apex at approximately 60% (+/-10%) of the
chord length of the pressure side 206 (+/-10%). In this case, the
depression in the pressure trough 250 can span approximately 40-60%
pitch as measured from the pressure side 206.
It is understood that in various embodiments, other apex locations
and pitches are possible, and those values given herein are merely
illustrative of several of the many possible embodiments in
accordance with the disclosure.
With reference to FIG. 4 (and continuing reference to FIGS. 2-3), a
plurality of points 270-278 along span S, including root 215 and
tip 217, can correspond to Z coordinate values of chord lines, and
a cross section of airfoil 202 at each point can be described by a
respective set of X and Y coordinates. For example, 100 points can
be listed for each cross section 270-278, though it should be
apparent that more or fewer points can be used for each cross
section, and more or fewer cross sections can be used, as may be
desired and/or appropriate. The X, Y, and Z coordinate values in
TABLE I have been expressed in normalized or non-dimensionalized
form in values of from 0 to 1, but it should be apparent that any
or all of the coordinate values could instead be expressed in
distance units so long as the proportions are maintained. To
convert an X, Y or Z value of TABLE I to a respective X, Y or Z
coordinate value in units of distance, such as inches or meters,
the non-dimensional X, Y or Z value given in TABLE I can be
multiplied by a trailing edge height of airfoil 202 in such units
of distance. By connecting the X and Y values with smooth
continuing arcs, each profile cross section at each distance Z can
be fixed, and the airfoil profiles of the various surface locations
between the distances Z can be determined by smoothly connecting
adjacent profile sections to one another, thus forming the airfoil
profile.
The values in TABLE I are generated and shown to four decimal
places for determining the profile of at least one of a suction
side or a pressure side of a nominal airfoil 202 at ambient,
non-operating, or non-hot conditions, and do not take any coatings
or fillets into account, though embodiments could account for other
conditions, coatings, and/or fillets. To allow for typical
manufacturing tolerances and/or coating thicknesses, .+-.values can
be added to the values listed in TABLE I, particularly to the X and
Y values therein. For example, a tolerance of about 10-20percent of
a thickness of the trailing edge in a direction normal to any
surface location along the airfoil profile can define an airfoil
profile envelope for a nozzle airfoil design at cold or room
temperature. In other words, a distance of about 10-20 percent of a
thickness of the trailing edge in a direction normal to any surface
location along the airfoil profile can define a range of variation
between measured points on an actual airfoil surface and ideal
positions of those points, particularly at a cold or room
temperature, as embodied by the invention. The nozzle airfoil
design, as embodied by the invention, is robust to this range of
variation without impairment of mechanical and aerodynamic
functions. Likewise, the profile and/or design can be scaled up or
down, such as geometrically, without impairment of operation, and
such scaling can be facilitated by use of normalized coordinate
values, i.e. multiplying the normalized values by a scaling factor,
or a larger or smaller number of distance units than might have
originally been used. For example, the values in TABLE I,
particularly the X and Y values, could be multiplied by a scaling
factor of 2, 0.5, or any other desired scaling factor.
Alternatively, the values could be multiplied by a larger or
smaller desired span. As referenced herein, the origin of the X, Y,
Z coordinate system is the root of the leading edge (junction 232)
of the airfoil 202.
TABLE-US-00001 TABLE I Non-Dimensionalized (X Y Z/Span Height) N
Location X Y Z 1 Suction-Side -0.00776 -0.02251 0.00000 2
Suction-Side -0.00609 -0.01050 0.00000 3 Suction-Side -0.00579
-0.03453 0.00000 4 Suction-Side -0.00171 -0.04602 0.00000 5
Suction-Side 0.00000 0.00000 0.00000 6 Suction-Side 0.00363
-0.05698 0.00000 7 Suction-Side 0.00979 -0.06752 0.00000 8
Suction-Side 0.01656 -0.07768 0.00000 9 Suction-Side 0.02380
-0.08750 0.00000 10 Suction-Side 0.03143 -0.09703 0.00000 11
Suction-Side 0.03938 -0.10628 0.00000 12 Suction-Side 0.04764
-0.11526 0.00000 13 Suction-Side 0.05617 -0.12398 0.00000 14
Suction-Side 0.06497 -0.13244 0.00000 15 Suction-Side 0.07401
-0.14063 0.00000 16 Suction-Side 0.08330 -0.14855 0.00000 17
Suction-Side 0.09281 -0.15619 0.00000 18 Suction-Side 0.10257
-0.16353 0.00000 19 Suction-Side 0.11255 -0.17056 0.00000 20
Suction-Side 0.12275 -0.17724 0.00000 21 Suction-Side 0.13317
-0.18358 0.00000 22 Suction-Side 0.14383 -0.18955 0.00000 23
Suction-Side 0.15469 -0.19510 0.00000 24 Suction-Side 0.16577
-0.20022 0.00000 25 Suction-Side 0.17705 -0.20487 0.00000 26
Suction-Side 0.18852 -0.20902 0.00000 27 Suction-Side 0.20018
-0.21263 0.00000 28 Suction-Side 0.21199 -0.21567 0.00000 29
Suction-Side 0.22395 -0.21811 0.00000 30 Suction-Side 0.23602
-0.21991 0.00000 31 Suction-Side 0.24818 -0.22104 0.00000 32
Suction-Side 0.26037 -0.22147 0.00000 33 Suction-Side 0.27257
-0.22120 0.00000 34 Suction-Side 0.28473 -0.22021 0.00000 35
Suction-Side 0.29681 -0.21848 0.00000 36 Suction-Side 0.30877
-0.21605 0.00000 37 Suction-Side 0.32055 -0.21291 0.00000 38
Suction-Side 0.33216 -0.20911 0.00000 39 Suction-Side 0.34352
-0.20467 0.00000 40 Suction-Side 0.35463 -0.19962 0.00000 41
Suction-Side 0.36547 -0.19403 0.00000 42 Suction-Side 0.37602
-0.18790 0.00000 43 Suction-Side 0.38628 -0.18129 0.00000 44
Suction-Side 0.39625 -0.17425 0.00000 45 Suction-Side 0.40592
-0.16682 0.00000 46 Suction-Side 0.41531 -0.15901 0.00000 47
Suction-Side 0.42440 -0.15087 0.00000 48 Suction-Side 0.43322
-0.14244 0.00000 49 Suction-Side 0.44177 -0.13373 0.00000 50
Suction-Side 0.45006 -0.12477 0.00000 51 Suction-Side 0.45810
-0.11560 0.00000 52 Suction-Side 0.46591 -0.10622 0.00000 53
Suction-Side 0.47350 -0.09667 0.00000 54 Suction-Side 0.48088
-0.08694 0.00000 55 Suction-Side 0.48805 -0.07707 0.00000 56
Suction-Side 0.49503 -0.06706 0.00000 57 Suction-Side 0.50182
-0.05692 0.00000 58 Suction-Side 0.50844 -0.04666 0.00000 59
Suction-Side 0.51488 -0.03631 0.00000 60 Suction-Side 0.52117
-0.02585 0.00000 61 Suction-Side 0.52731 -0.01530 0.00000 62
Suction-Side 0.53332 -0.00468 0.00000 63 Suction-Side 0.53918
0.00603 0.00000 64 Suction-Side 0.54492 0.01680 0.00000 65
Suction-Side 0.55053 0.02764 0.00000 66 Suction-Side 0.55603
0.03854 0.00000 67 Suction-Side 0.56141 0.04949 0.00000 68
Suction-Side 0.56670 0.06048 0.00000 69 Suction-Side 0.57188
0.07154 0.00000 70 Suction-Side 0.57697 0.08262 0.00000 71
Suction-Side 0.58198 0.09376 0.00000 72 Suction-Side 0.58690
0.10492 0.00000 73 Suction-Side 0.59175 0.11612 0.00000 74
Suction-Side 0.59651 0.12735 0.00000 75 Suction-Side 0.60121
0.13862 0.00000 76 Suction-Side 0.60584 0.14990 0.00000 77
Suction-Side 0.61041 0.16123 0.00000 78 Suction-Side 0.61491
0.17256 0.00000 79 Suction-Side 0.61935 0.18394 0.00000 80
Suction-Side 0.62375 0.19531 0.00000 81 Suction-Side 0.62810
0.20672 0.00000 82 Suction-Side 0.63240 0.21815 0.00000 83
Suction-Side 0.63665 0.22959 0.00000 84 Suction-Side 0.64085
0.24103 0.00000 85 Suction-Side 0.64503 0.25251 0.00000 86
Suction-Side 0.64916 0.26399 0.00000 87 Suction-Side 0.65324
0.27549 0.00000 88 Suction-Side 0.65729 0.28700 0.00000 89
Suction-Side 0.66131 0.29852 0.00000 90 Suction-Side 0.66528
0.31007 0.00000 91 Suction-Side 0.66923 0.32162 0.00000 92
Suction-Side 0.67315 0.33317 0.00000 93 Suction-Side 0.67703
0.34474 0.00000 94 Suction-Side 0.67998 0.40050 0.00000 95
Suction-Side 0.68088 0.35632 0.00000 96 Suction-Side 0.68470
0.36790 0.00000 97 Suction-Side 0.68507 0.39694 0.00000 98
Suction-Side 0.68842 0.39172 0.00000 99 Suction-Side 0.68850
0.37951 0.00000 100 Suction-Side 0.68960 0.38562 0.00000 101
Pressure-Side 0.00000 0.00000 0.00000 102 Pressure-Side 0.00627
0.00621 0.00000 103 Pressure-Side 0.01352 0.01123 0.00000 104
Pressure-Side 0.02146 0.01507 0.00000 105 Pressure-Side 0.02983
0.01785 0.00000 106 Pressure-Side 0.03845 0.01977 0.00000 107
Pressure-Side 0.04718 0.02104 0.00000 108 Pressure-Side 0.05597
0.02177 0.00000 109 Pressure-Side 0.06480 0.02213 0.00000 110
Pressure-Side 0.07362 0.02218 0.00000 111 Pressure-Side 0.08246
0.02202 0.00000 112 Pressure-Side 0.09128 0.02170 0.00000 113
Pressure-Side 0.10010 0.02126 0.00000 114 Pressure-Side 0.10891
0.02076 0.00000 115 Pressure-Side 0.11772 0.02020 0.00000 116
Pressure-Side 0.12653 0.01964 0.00000 117 Pressure-Side 0.13534
0.01908 0.00000 118 Pressure-Side 0.14416 0.01855 0.00000 119
Pressure-Side 0.15297 0.01806 0.00000 120 Pressure-Side 0.16180
0.01762 0.00000 121 Pressure-Side 0.17061 0.01726 0.00000 122
Pressure-Side 0.17943 0.01700 0.00000 123 Pressure-Side 0.18827
0.01681 0.00000 124 Pressure-Side 0.19709 0.01674 0.00000 125
Pressure-Side 0.20592 0.01680 0.00000 126 Pressure-Side 0.21474
0.01697 0.00000 127 Pressure-Side 0.22357 0.01728 0.00000 128
Pressure-Side 0.23239 0.01773 0.00000 129 Pressure-Side 0.24120
0.01833 0.00000 130 Pressure-Side 0.25000 0.01910 0.00000 131
Pressure-Side 0.25877 0.02001 0.00000 132 Pressure-Side 0.26754
0.02110 0.00000 133 Pressure-Side 0.27627 0.02238 0.00000 134
Pressure-Side 0.28498 0.02383 0.00000 135 Pressure-Side 0.29366
0.02546 0.00000 136 Pressure-Side 0.30229 0.02728 0.00000 137
Pressure-Side 0.31089 0.02930 0.00000 138 Pressure-Side 0.31944
0.03151 0.00000 139 Pressure-Side 0.32793 0.03393 0.00000 140
Pressure-Side 0.33637 0.03653 0.00000 141 Pressure-Side 0.34474
0.03934 0.00000 142 Pressure-Side 0.35305 0.04233 0.00000 143
Pressure-Side 0.36127 0.04553 0.00000 144 Pressure-Side 0.36942
0.04893 0.00000 145 Pressure-Side 0.37749 0.05252 0.00000 146
Pressure-Side 0.38546 0.05631 0.00000 147 Pressure-Side 0.39335
0.06028 0.00000 148 Pressure-Side 0.40113 0.06444 0.00000 149
Pressure-Side 0.40882 0.06879 0.00000 150 Pressure-Side 0.41640
0.07332 0.00000 151 Pressure-Side 0.42387 0.07801 0.00000 152
Pressure-Side 0.43123 0.08289 0.00000 153 Pressure-Side 0.43848
0.08792 0.00000 154 Pressure-Side 0.44562 0.09312 0.00000 155
Pressure-Side 0.45265 0.09847 0.00000 156 Pressure-Side 0.45955
0.10398 0.00000 157 Pressure-Side 0.46635 0.10961 0.00000 158
Pressure-Side 0.47302 0.11539 0.00000 159 Pressure-Side 0.47959
0.12129 0.00000 160 Pressure-Side 0.48603 0.12733 0.00000 161
Pressure-Side 0.49236 0.13348 0.00000 162 Pressure-Side 0.49858
0.13975 0.00000 163 Pressure-Side 0.50468 0.14613 0.00000 164
Pressure-Side 0.51067 0.15260 0.00000 165 Pressure-Side 0.51656
0.15919 0.00000 166 Pressure-Side 0.52234 0.16586 0.00000 167
Pressure-Side 0.52801 0.17263 0.00000 168 Pressure-Side 0.53358
0.17947 0.00000 169 Pressure-Side 0.53906 0.18641 0.00000 170
Pressure-Side 0.54443 0.19341 0.00000 171 Pressure-Side 0.54970
0.20050 0.00000 172 Pressure-Side 0.55490 0.20763 0.00000 173
Pressure-Side 0.55999 0.21485 0.00000 174 Pressure-Side 0.56500
0.22212 0.00000 175 Pressure-Side 0.56993 0.22944 0.00000 176
Pressure-Side 0.57478 0.23682 0.00000 177 Pressure-Side 0.57954
0.24426 0.00000 178 Pressure-Side 0.58423 0.25173 0.00000 179
Pressure-Side 0.58885 0.25926 0.00000 180 Pressure-Side 0.59340
0.26682 0.00000 181 Pressure-Side 0.59789 0.27443 0.00000 182
Pressure-Side 0.60230 0.28207 0.00000 183 Pressure-Side 0.60666
0.28975 0.00000 184 Pressure-Side 0.61097 0.29746 0.00000 185
Pressure-Side 0.61522 0.30519 0.00000 186 Pressure-Side 0.61942
0.31297 0.00000 187 Pressure-Side 0.62356 0.32075 0.00000 188
Pressure-Side 0.62767 0.32857 0.00000 189 Pressure-Side 0.63174
0.33641 0.00000 190 Pressure-Side 0.63576 0.34426 0.00000 191
Pressure-Side 0.63976 0.35214 0.00000 192 Pressure-Side 0.64372
0.36002 0.00000 193 Pressure-Side 0.64766 0.36793 0.00000 194
Pressure-Side 0.65157 0.37585 0.00000 195 Pressure-Side 0.65547
0.38377 0.00000 196 Pressure-Side 0.65938 0.39169 0.00000 197
Pressure-Side 0.66277 0.39690 0.00000 198 Pressure-Side 0.66784
0.40048 0.00000 199 Pressure-Side 0.67390 0.40175 0.00000 200
Pressure-Side 0.67998 0.40050 0.00000 1 Suction-Side -0.01641
-0.01591 0.10000 2 Suction-Side -0.01565 -0.02816 0.10000 3
Suction-Side -0.01357 -0.00399 0.10000 4 Suction-Side -0.01241
-0.04003 0.10000 5 Suction-Side -0.00760 -0.05135 0.10000 6
Suction-Side -0.00707 0.00642 0.10000 7 Suction-Side -0.00173
-0.06217 0.10000 8 Suction-Side 0.00489 -0.07255 0.10000 9
Suction-Side 0.01208 -0.08254 0.10000 10 Suction-Side 0.01972
-0.09219 0.10000 11 Suction-Side 0.02777 -0.10150 0.10000 12
Suction-Side 0.03616 -0.11051 0.10000 13 Suction-Side 0.04486
-0.11922 0.10000 14 Suction-Side 0.05386 -0.12763 0.10000 15
Suction-Side 0.06312 -0.13574 0.10000 16 Suction-Side 0.07265
-0.14353 0.10000 17 Suction-Side 0.08243 -0.15101 0.10000 18
Suction-Side 0.09247 -0.15816 0.10000 19 Suction-Side 0.10273
-0.16496 0.10000 20 Suction-Side 0.11321 -0.17139 0.10000 21
Suction-Side 0.12394 -0.17744 0.10000 22 Suction-Side 0.13489
-0.18307 0.10000 23 Suction-Side 0.14605 -0.18828 0.10000 24
Suction-Side 0.15741 -0.19302 0.10000 25 Suction-Side 0.16897
-0.19724 0.10000 26 Suction-Side 0.18072 -0.20094 0.10000 27
Suction-Side 0.19262 -0.20407 0.10000 28 Suction-Side 0.20467
-0.20660 0.10000 29 Suction-Side 0.21683 -0.20850 0.10000 30
Suction-Side 0.22908 -0.20973 0.10000 31 Suction-Side 0.24138
-0.21029 0.10000 32 Suction-Side 0.25369 -0.21015 0.10000 33
Suction-Side 0.26597 -0.20927 0.10000 34 Suction-Side 0.27817
-0.20769 0.10000 35 Suction-Side 0.29027 -0.20539 0.10000 36
Suction-Side 0.30221 -0.20240 0.10000 37 Suction-Side 0.31396
-0.19872 0.10000 38 Suction-Side 0.32548 -0.19440 0.10000 39
Suction-Side 0.33677 -0.18948 0.10000 40 Suction-Side 0.34778
-0.18398 0.10000 41 Suction-Side 0.35852 -0.17794 0.10000 42
Suction-Side 0.36897 -0.17143 0.10000 43 Suction-Side 0.37912
-0.16447 0.10000 44 Suction-Side 0.38897 -0.15709 0.10000 45
Suction-Side 0.39854 -0.14933 0.10000
46 Suction-Side 0.40781 -0.14124 0.10000 47 Suction-Side 0.41680
-0.13283 0.10000 48 Suction-Side 0.42551 -0.12412 0.10000 49
Suction-Side 0.43397 -0.11518 0.10000 50 Suction-Side 0.44216
-0.10600 0.10000 51 Suction-Side 0.45014 -0.09661 0.10000 52
Suction-Side 0.45787 -0.08703 0.10000 53 Suction-Side 0.46539
-0.07729 0.10000 54 Suction-Side 0.47272 -0.06739 0.10000 55
Suction-Side 0.47984 -0.05734 0.10000 56 Suction-Side 0.48676
-0.04718 0.10000 57 Suction-Side 0.49353 -0.03688 0.10000 58
Suction-Side 0.50011 -0.02647 0.10000 59 Suction-Side 0.50653
-0.01596 0.10000 60 Suction-Side 0.51280 -0.00537 0.10000 61
Suction-Side 0.51892 0.00532 0.10000 62 Suction-Side 0.52490
0.01607 0.10000 63 Suction-Side 0.53075 0.02690 0.10000 64
Suction-Side 0.53649 0.03780 0.10000 65 Suction-Side 0.54210
0.04876 0.10000 66 Suction-Side 0.54760 0.05978 0.10000 67
Suction-Side 0.55300 0.07083 0.10000 68 Suction-Side 0.55830
0.08196 0.10000 69 Suction-Side 0.56350 0.09311 0.10000 70
Suction-Side 0.56861 0.10431 0.10000 71 Suction-Side 0.57365
0.11555 0.10000 72 Suction-Side 0.57859 0.12682 0.10000 73
Suction-Side 0.58346 0.13813 0.10000 74 Suction-Side 0.58825
0.14947 0.10000 75 Suction-Side 0.59299 0.16084 0.10000 76
Suction-Side 0.59765 0.17223 0.10000 77 Suction-Side 0.60225
0.18365 0.10000 78 Suction-Side 0.60679 0.19509 0.10000 79
Suction-Side 0.61129 0.20656 0.10000 80 Suction-Side 0.61572
0.21804 0.10000 81 Suction-Side 0.62011 0.22955 0.10000 82
Suction-Side 0.62444 0.24107 0.10000 83 Suction-Side 0.62873
0.25260 0.10000 84 Suction-Side 0.63299 0.26417 0.10000 85
Suction-Side 0.63720 0.27573 0.10000 86 Suction-Side 0.64137
0.28732 0.10000 87 Suction-Side 0.64549 0.29892 0.10000 88
Suction-Side 0.64959 0.31053 0.10000 89 Suction-Side 0.65363
0.32216 0.10000 90 Suction-Side 0.65764 0.33380 0.10000 91
Suction-Side 0.66161 0.34546 0.10000 92 Suction-Side 0.66556
0.35711 0.10000 93 Suction-Side 0.66947 0.36879 0.10000 94
Suction-Side 0.67228 0.42474 0.10000 95 Suction-Side 0.67335
0.38048 0.10000 96 Suction-Side 0.67719 0.39217 0.10000 97
Suction-Side 0.67744 0.42127 0.10000 98 Suction-Side 0.68084
0.41609 0.10000 99 Suction-Side 0.68100 0.40388 0.10000 100
Suction-Side 0.68206 0.41000 0.10000 101 Pressure-Side -0.00707
0.00642 0.10000 102 Pressure-Side -0.00072 0.01261 0.10000 103
Pressure-Side 0.00671 0.01749 0.10000 104 Pressure-Side 0.01483
0.02109 0.10000 105 Pressure-Side 0.02334 0.02364 0.10000 106
Pressure-Side 0.03205 0.02538 0.10000 107 Pressure-Side 0.04088
0.02651 0.10000 108 Pressure-Side 0.04973 0.02722 0.10000 109
Pressure-Side 0.05862 0.02758 0.10000 110 Pressure-Side 0.06751
0.02768 0.10000 111 Pressure-Side 0.07640 0.02764 0.10000 112
Pressure-Side 0.08528 0.02747 0.10000 113 Pressure-Side 0.09417
0.02722 0.10000 114 Pressure-Side 0.10306 0.02692 0.10000 115
Pressure-Side 0.11194 0.02661 0.10000 116 Pressure-Side 0.12083
0.02630 0.10000 117 Pressure-Side 0.12970 0.02602 0.10000 118
Pressure-Side 0.13860 0.02578 0.10000 119 Pressure-Side 0.14749
0.02561 0.10000 120 Pressure-Side 0.15638 0.02550 0.10000 121
Pressure-Side 0.16527 0.02548 0.10000 122 Pressure-Side 0.17416
0.02556 0.10000 123 Pressure-Side 0.18305 0.02573 0.10000 124
Pressure-Side 0.19193 0.02602 0.10000 125 Pressure-Side 0.20080
0.02645 0.10000 126 Pressure-Side 0.20968 0.02699 0.10000 127
Pressure-Side 0.21854 0.02768 0.10000 128 Pressure-Side 0.22739
0.02852 0.10000 129 Pressure-Side 0.23623 0.02952 0.10000 130
Pressure-Side 0.24504 0.03066 0.10000 131 Pressure-Side 0.25384
0.03197 0.10000 132 Pressure-Side 0.26260 0.03346 0.10000 133
Pressure-Side 0.27133 0.03512 0.10000 134 Pressure-Side 0.28003
0.03697 0.10000 135 Pressure-Side 0.28869 0.03900 0.10000 136
Pressure-Side 0.29730 0.04121 0.10000 137 Pressure-Side 0.30586
0.04360 0.10000 138 Pressure-Side 0.31436 0.04619 0.10000 139
Pressure-Side 0.32280 0.04897 0.10000 140 Pressure-Side 0.33118
0.05195 0.10000 141 Pressure-Side 0.33949 0.05511 0.10000 142
Pressure-Side 0.34772 0.05847 0.10000 143 Pressure-Side 0.35588
0.06201 0.10000 144 Pressure-Side 0.36394 0.06574 0.10000 145
Pressure-Side 0.37193 0.06965 0.10000 146 Pressure-Side 0.37981
0.07376 0.10000 147 Pressure-Side 0.38761 0.07804 0.10000 148
Pressure-Side 0.39529 0.08249 0.10000 149 Pressure-Side 0.40288
0.08713 0.10000 150 Pressure-Side 0.41036 0.09194 0.10000 151
Pressure-Side 0.41774 0.09691 0.10000 152 Pressure-Side 0.42499
0.10204 0.10000 153 Pressure-Side 0.43214 0.10731 0.10000 154
Pressure-Side 0.43917 0.11275 0.10000 155 Pressure-Side 0.44610
0.11833 0.10000 156 Pressure-Side 0.45290 0.12404 0.10000 157
Pressure-Side 0.45960 0.12990 0.10000 158 Pressure-Side 0.46618
0.13587 0.10000 159 Pressure-Side 0.47265 0.14197 0.10000 160
Pressure-Side 0.47902 0.14818 0.10000 161 Pressure-Side 0.48526
0.15450 0.10000 162 Pressure-Side 0.49140 0.16092 0.10000 163
Pressure-Side 0.49744 0.16746 0.10000 164 Pressure-Side 0.50336
0.17409 0.10000 165 Pressure-Side 0.50917 0.18082 0.10000 166
Pressure-Side 0.51488 0.18762 0.10000 167 Pressure-Side 0.52049
0.19452 0.10000 168 Pressure-Side 0.52601 0.20149 0.10000 169
Pressure-Side 0.53143 0.20854 0.10000 170 Pressure-Side 0.53675
0.21566 0.10000 171 Pressure-Side 0.54198 0.22285 0.10000 172
Pressure-Side 0.54712 0.23009 0.10000 173 Pressure-Side 0.55219
0.23740 0.10000 174 Pressure-Side 0.55717 0.24478 0.10000 175
Pressure-Side 0.56206 0.25219 0.10000 176 Pressure-Side 0.56689
0.25966 0.10000 177 Pressure-Side 0.57163 0.26718 0.10000 178
Pressure-Side 0.57631 0.27474 0.10000 179 Pressure-Side 0.58092
0.28235 0.10000 180 Pressure-Side 0.58545 0.28999 0.10000 181
Pressure-Side 0.58993 0.29767 0.10000 182 Pressure-Side 0.59434
0.30539 0.10000 183 Pressure-Side 0.59870 0.31314 0.10000 184
Pressure-Side 0.60301 0.32091 0.10000 185 Pressure-Side 0.60726
0.32873 0.10000 186 Pressure-Side 0.61146 0.33655 0.10000 187
Pressure-Side 0.61562 0.34442 0.10000 188 Pressure-Side 0.61972
0.35230 0.10000 189 Pressure-Side 0.62380 0.36020 0.10000 190
Pressure-Side 0.62784 0.36812 0.10000 191 Pressure-Side 0.63186
0.37605 0.10000 192 Pressure-Side 0.63583 0.38400 0.10000 193
Pressure-Side 0.63979 0.39196 0.10000 194 Pressure-Side 0.64372
0.39993 0.10000 195 Pressure-Side 0.64765 0.40790 0.10000 196
Pressure-Side 0.65155 0.41589 0.10000 197 Pressure-Side 0.65502
0.42105 0.10000 198 Pressure-Side 0.66012 0.42460 0.10000 199
Pressure-Side 0.66620 0.42589 0.10000 200 Pressure-Side 0.67228
0.42474 0.10000 1 Suction-Side -0.02579 -0.00894 0.20001 2
Suction-Side -0.02522 -0.02136 0.20001 3 Suction-Side -0.02280
0.00310 0.20001 4 Suction-Side -0.02211 -0.03340 0.20001 5
Suction-Side -0.01736 -0.04490 0.20001 6 Suction-Side -0.01619
0.01360 0.20001 7 Suction-Side -0.01147 -0.05588 0.20001 8
Suction-Side -0.00477 -0.06638 0.20001 9 Suction-Side 0.00256
-0.07645 0.20001 10 Suction-Side 0.01042 -0.08612 0.20001 11
Suction-Side 0.01871 -0.09542 0.20001 12 Suction-Side 0.02738
-0.10436 0.20001 13 Suction-Side 0.03640 -0.11296 0.20001 14
Suction-Side 0.04573 -0.12121 0.20001 15 Suction-Side 0.05536
-0.12911 0.20001 16 Suction-Side 0.06528 -0.13665 0.20001 17
Suction-Side 0.07546 -0.14383 0.20001 18 Suction-Side 0.08589
-0.15064 0.20001 19 Suction-Side 0.09656 -0.15705 0.20001 20
Suction-Side 0.10748 -0.16305 0.20001 21 Suction-Side 0.11862
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According to various embodiments, and as a result of endwall
contour 218, a region of a passage trough 250 between two airfoils
202 proximate endwall 212 can be affected. For example, a bottom
edge of a passage trough 250 between a pair of nozzles 200 can vary
radially, whereas an endwall without a contour would leave a bottom
edge of such a throat as at least a straight line, if not a
substantially constant radial distance.
Turning to FIG. 5, a schematic view of portions of a multi-shaft
combined cycle power plant 900 is shown. Combined cycle power plant
900 may include, for example, a gas turbine 980 operably connected
to a generator 970. Generator 970 and gas turbine 980 may be
mechanically coupled by a shaft 915, which may transfer energy
between a drive shaft (not shown) of gas turbine 980 and generator
970. Also shown in FIG. 5 is a heat exchanger 986 operably
connected to gas turbine 980 and a steam turbine 992. Heat
exchanger 986 may be fluidly connected to both gas turbine 980 and
a steam turbine 992 via conventional conduits (numbering omitted).
Gas turbine 980 and/or steam turbine 992 may include one or more
nozzles 200 as shown and described with reference to FIG. 2 and/or
other embodiments described herein. Heat exchanger 986 may be a
conventional heat recovery steam generator (HRSG), such as those
used in conventional combined cycle power systems. As is known in
the art of power generation, HRSG 986 may use hot exhaust from gas
turbine 980, combined with a water supply, to create steam which is
fed to steam turbine 992. Steam turbine 992 may optionally be
coupled to a second generator system 970 (via a second shaft 915).
It is understood that generators 970 and shafts 915 may be of any
size or type known in the art and may differ depending upon their
application or the system to which they are connected. Common
numbering of the generators and shafts is for clarity and does not
necessarily suggest these generators or shafts are identical. In
another embodiment, shown in FIG. 6, a single shaft combined cycle
power plant 990 may include a single generator 970 coupled to both
gas turbine 980 and steam turbine 992 via a single shaft 915. Steam
turbine 992 and/or gas turbine 980 may include one or more nozzles
200 shown and described with reference to FIG. 2 and/or other
embodiments described herein.
The apparatus and devices of the present disclosure are not limited
to any one particular engine, turbine, jet engine, generator, power
generation system or other system, and may be used with other
aircraft systems, power generation systems and/or systems (e.g.,
combined cycle, simple cycle, nuclear reactor, etc.). Additionally,
the apparatus of the present invention may be used with other
systems not described herein that may benefit from the increased
efficiency of the apparatus and devices described herein.
In various embodiments, components described as being "coupled" to
one another can be joined along one or more interfaces. In some
embodiments, these interfaces can include junctions between
distinct components, and in other cases, these interfaces can
include a solidly and/or integrally formed interconnection. That
is, in some cases, components that are "coupled" to one another can
be simultaneously formed to define a single continuous member.
However, in other embodiments, these coupled components can be
formed as separate members and be subsequently joined through known
processes (e.g., fastening, ultrasonic welding, bonding).
The terminology used herein is for the purpose of describing
particular example embodiments only and is not intended to be
limiting. As used herein, the singular forms "a", "an" and "the"
may be intended to include the plural forms as well, unless the
context clearly indicates otherwise. The terms "comprises,"
"comprising," "including," and "having," are inclusive and
therefore specify the presence of stated features, integers, steps,
operations, elements, and/or components, but do not preclude the
presence or addition of one or more other features, integers,
steps, operations, elements, components, and/or groups thereof. The
method steps, processes, and operations described herein are not to
be construed as necessarily requiring their performance in the
particular order discussed or illustrated, unless specifically
identified as an order of performance. It is also to be understood
that additional or alternative steps may be employed.
When an element or layer is referred to as being "on", "engaged
to", "connected to" or "coupled to" another element or layer, it
may be directly on, engaged, connected or coupled to the other
element or layer, or intervening elements or layers may be present.
In contrast, when an element is referred to as being "directly on,"
"directly engaged to", "directly connected to" or "directly coupled
to" another element or layer, there may be no intervening elements
or layers present. Other words used to describe the relationship
between elements should be interpreted in a like fashion (e.g.,
"between" versus "directly between," "adjacent" versus "directly
adjacent," etc.). As used herein, the term "and/or" includes any
and all combinations of one or more of the associated listed
items.
Spatially relative terms, such as "inner," "outer," "beneath",
"below", "lower", "above", "upper" and the like, may be used herein
for ease of description to describe one element or feature's
relationship to another element(s) or feature(s) as illustrated in
the figures. Spatially relative terms may be intended to encompass
different orientations of the device in use or operation in
addition to the orientation depicted in the figures. For example,
if the device in the figures is turned over, elements described as
"below" or "beneath" other elements or features would then be
oriented "above" the other elements or features. Thus, the example
term "below" can encompass both an orientation of above and below.
The device may be otherwise oriented (rotated 90 degrees or at
other orientations) and the spatially relative descriptors used
herein interpreted accordingly.
The foregoing description of various aspects of the invention has
been presented for purposes of illustration and description. It is
not intended to be exhaustive or to limit the invention to the
precise form disclosed, and obviously, many modifications and
variations are possible. Such modifications and variations that may
be apparent to an individual in the art are included within the
scope of the invention as defined by the accompanying claims.
This written description uses examples to disclose the invention,
including the best mode, and also to enable any person skilled in
the art to practice the invention, including making and using any
devices or systems and performing any incorporated methods. The
patentable scope of the invention is defined by the claims, and may
include other examples that occur to those skilled in the art. Such
other examples are intended to be within the scope of the claims if
they have structural elements that do not differ from the literal
language of the claims, or if they include equivalent structural
elements with insubstantial differences from the literal languages
of the claims.
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